Transition duct having airfoil and hot gas path assembly for turbomachine

Abstract

Transition ducts, hot gas path assemblies, and turbomachines are provided. A hot gas path assembly includes an outer support ring, an inner support ring, and a transition duct coupled to the outer support ring and the inner support ring. The transition duct includes a conduit defining a passage extending between an inlet and an outlet. The inlet and the outlet are generally aligned along a longitudinal axis. The transition duct further includes an airfoil disposed within the conduit and configured to alter a hot gas flow direction.

What is claimed is: 
     
         1 . A hot gas path assembly, comprising:
 an outer support ring;   an inner support ring; and   a transition duct coupled to the outer support ring and the inner support ring, the transition duct comprising a conduit defining a passage extending between an inlet and an outlet, the inlet and the outlet generally aligned along a longitudinal axis, the transition duct further comprising an airfoil disposed within the conduit and configured to alter a hot gas flow direction.   
     
     
         2 . The hot gas path assembly of  claim 1 , wherein the inlet has an oval cross-sectional shape and the outlet has a quadrilateral cross-sectional shape. 
     
     
         3 . The hot gas path assembly of  claim 1 , wherein the quadrilateral cross-sectional shape is a rectangular cross-sectional shape. 
     
     
         4 . The hot gas path assembly of  claim 1 , wherein opposing cut-away portions are defined in the conduit, each of the opposing cut-away portions extending from the outlet, and defined by a plurality of sidewalls, each of the plurality of sidewalls configured for contacting a corresponding sidewall of an adjacent transition duct. 
     
     
         5 . The hot gas path assembly of  claim 4 , wherein each of the plurality of sidewalls defines a channel therein, and further comprising a seal member disposed in each of the plurality of channels. 
     
     
         6 . The hot gas path assembly of  claim 1 , wherein the conduit further comprises an inner interface feature and an outer interface feature, each of the inner and outer interface features extending from an outer surface of the conduit, the inner interface feature coupled to the inner support ring, the outer interface feature coupled to the outer support ring. 
     
     
         7 . The hot gas path assembly of  claim 1 , wherein the airfoil is a plurality of airfoils. 
     
     
         8 . A transition duct for a gas turbine system, comprising:
 a conduit defining a passage extending between an inlet and an outlet, the inlet and the outlet generally aligned along a longitudinal axis; and   an airfoil disposed within the conduit and configured to alter a hot gas flow direction.   
     
     
         9 . The transition duct of  claim 8 , wherein the inlet has an oval cross-sectional shape and the outlet has a quadrilateral cross-sectional shape. 
     
     
         10 . The transition duct of  claim 8 , wherein the quadrilateral cross-sectional shape is a rectangular cross-sectional shape. 
     
     
         11 . The transition duct of  claim 8 , wherein opposing cut-away portions are defined in the conduit, each of the opposing cut-away portions extending from the outlet, and defined by a plurality of sidewalls. 
     
     
         12 . The transition duct of  claim 11 , wherein each of the plurality of sidewalls defines a channel therein, the channel configured to accommodate a seal member. 
     
     
         13 . The transition duct of  claim 8 , wherein the conduit further comprises a plurality of interface features, each of the plurality of interface features extending from an outer surface of the conduit, each of the plurality of interface features configured for interfacing with one of an outer support ring or an inner support ring. 
     
     
         14 . The transition duct of  claim 8 , wherein the airfoil is a plurality of airfoils. 
     
     
         15 . A turbomachine, comprising:
 an inlet section;   an exhaust section;   a compressor section;   a combustor section;   a turbine section; and   a plurality of hot gas path assemblies disposed within and extending between the combustor section and the turbine section, each of the plurality of hot gas path assemblies comprising:
 an outer support ring; 
 an inner support ring; and 
 a transition duct coupled to the outer support ring and the inner support ring, the transition duct comprising a conduit defining a passage extending between an inlet and an outlet, the inlet and the outlet generally aligned along a longitudinal axis, the transition duct further comprising an airfoil disposed within the conduit and configured to alter a hot gas flow direction. 
   
     
     
         16 . The turbomachine of  claim 15 , wherein the inlet has an oval cross-sectional shape and the outlet has a quadrilateral cross-sectional shape. 
     
     
         17 . The turbomachine of  claim 15 , wherein the quadrilateral cross-sectional shape is a rectangular cross-sectional shape. 
     
     
         18 . The turbomachine of  claim 15 , wherein opposing cut-away portions are defined in the conduit, each of the opposing cut-away portions extending from the outlet, and defined by a plurality of sidewalls, each of the plurality of sidewalls configured for contacting a corresponding sidewall of an adjacent transition duct. 
     
     
         19 . The turbomachine of  claim 18 , wherein each of the plurality of sidewalls defines a channel therein, and further comprising a seal member disposed in each of the plurality of channels. 
     
     
         20 . The turbomachine of  claim 15 , wherein the conduit further comprises an inner interface feature and an outer interface feature, each of the inner and outer interface features extending from an outer surface of the conduit, the inner interface feature coupled to the inner support ring, the outer interface feature coupled to the outer support ring.